CN108361110B

CN108361110B - Inlet mesh screen for aircraft engines

Info

Publication number: CN108361110B
Application number: CN201810078290.XA
Authority: CN
Inventors: T.伊列夫斯基; M.菲利科夫斯基; A.P.帕西茨尼
Original assignee: General Electric Co Polska Sp zoo
Current assignee: General Electric Co Polska Sp zoo
Priority date: 2017-01-27
Filing date: 2018-01-26
Publication date: 2022-07-08
Anticipated expiration: 2038-01-26
Also published as: EP3354879B1; US11084599B2; US20180215478A1; EP3354879A1; CN108361110A; PL420326A1

Abstract

An apparatus (50) for providing foreign object debris protection to an air inlet (34) of an aircraft engine (12). The apparatus (50) includes a frame (53) and a plurality of cross members (74, 84, 74, 174, 184, 274, 284, 374, 384). The cross-members (74, 84, 74, 174, 184, 274, 284, 374, 384) are positioned in the frame (53) to define a plurality of mesh screen openings (94). At least one of the cross-members (74, 84, 74, 174, 184, 274, 284, 374, 384) has an aerodynamically efficient cross-section.

Description

Inlet mesh screen for aircraft engine

Technical Field

The present invention relates to aircraft engine efficiency and, more particularly, to an aerodynamic device for an inlet Foreign Object Debris (FOD) mesh screen.

Background

An inlet mesh screen for preventing foreign object debris ("FOD") is necessary for protection against potential damage and clogging that may be caused by FOD. Conventional FOD screens are formed from wire having a generally cylindrical cross-section. Conventional mesh screens cause air resistance as the air passes through the mesh screen, resulting in reduced efficiency of the engine. There is therefore a need for an inlet mesh screen that is more aerodynamically efficient than conventional meshes formed generally of cylindrical wires.

Disclosure of Invention

This need is addressed by a mesh screen having aerodynamically efficient crossover components.

According to an aspect of the present invention, there is provided an apparatus for providing foreign object debris protection to an air inlet of an aircraft engine. The apparatus includes a frame and a plurality of cross members. The cross-member is positioned in the frame to define a plurality of mesh screen openings. At least one of the cross members has an aerodynamically efficient cross section.

An apparatus for providing foreign object debris protection to an air inlet of an aircraft engine, the apparatus comprising;

a frame;

a plurality of cross members positioned in the frame to define a plurality of mesh screen openings; and

wherein at least one of the cross sections has an aerodynamically efficient cross section.

Solution 2. the apparatus according to solution 1, characterized in that the cross member is tubular.

Solution 3. the apparatus of solution 2 wherein the frame is configured to support a mesh assembly formed by the tubular cross members.

Solution 4. the apparatus of solution 3 wherein the frame is further configured to support a web that is not configured to be heated.

Solution 5. the apparatus according to solution 4, wherein the tubular cross members are arranged in layers and positioned substantially parallel to each other.

Solution 6. the apparatus according to solution 5, characterized in that the tubes are arranged in two layers, such that the tubular cross members in each layer are parallel to the tubular cross members also in that layer, and the tubular cross members in each layer cross the tubular cross members of the other layer to form a mesh.

The apparatus of claim 6, wherein the mesh is configured to prevent foreign matter debris from entering the air inlet of the engine.

Solution 8. the apparatus of solution 7 wherein the tubular cross-members are in a first tier and solid wire links are positioned in a second tier such that the first tier and the second tier collectively define a mesh.

Solution 9. the apparatus of solution 1 wherein said aerodynamically efficient cross-section is tear-drop shaped.

Solution 10. the apparatus according to solution 9, wherein the tail of the cross-section is narrow.

Claim 11. the apparatus of claim 9, wherein the tail of the cross-section is pointed.

Claim 12. the apparatus of claim 9, wherein the tail of the cross-section is circular.

Solution 13. the apparatus of solution 1 wherein the aerodynamically efficient cross-section is substantially diamond shaped.

Claim 14 the apparatus of claim 13, wherein one end of the cross-section is substantially circular.

Claim 15 the apparatus of claim 14 wherein the two ends of the cross section are rounded.

An apparatus (50) for providing foreign object debris protection to an air inlet (34) of an aircraft engine (12), the apparatus (50) comprising;

a frame (53);

a plurality of cross-members (74, 84, 74, 174, 184, 274, 284, 374, 384) (74, 84, 74, 174, 184, 274, 284, 374, 384) positioned in the frame (53) to define a plurality of mesh screen openings (94); and

wherein at least one of the cross-members (74, 84, 74, 174, 184, 274, 284, 374, 384) has an aerodynamically efficient cross-section.

Claim 17 the apparatus (50) of claim 16, wherein the cross member (74, 84, 74, 174, 184, 274, 284, 374, 384) is tubular.

The apparatus (50) of claim 18, wherein the frame (53) is configured to support a mesh (55) assembly (70) formed by the tubular cross members (74, 84, 74, 174, 184, 274, 284, 374, 384).

Solution 19. the apparatus (50) according to solution 18, wherein the frame (53) is further configured to support a web (55) that is not configured to be heated.

Solution 20. apparatus (50) according to solution 19, characterized in that the tubular cross members (74, 84, 74, 174, 184, 274, 284, 374, 384) are arranged in layers (73) and positioned substantially parallel to each other.

Solution 21. the device (50) according to solution 20, characterized in that the tubular cross members (74, 84, 74, 174, 184, 274, 284, 374, 384) are arranged in two layers (73, 83) such that the tubular cross members (74, 84, 74, 174, 184, 274, 284, 374, 384) in each layer (73, 83) are parallel to the tubular cross members (74, 84, 74, 174, 184, 274, 284, 374, 384) also in that layer (73, 83), and that the tubular cross members (74, 84, 74, 174, 184, 274, 284, 374, 384) in each layer (73, 83) cross the tubular cross members (74, 84, 74, 174, 184, 274, 374, 384) of the other layer (73, 83) to form a mesh (55).

The apparatus (50) of claim 21, wherein the mesh (55) is configured to prevent foreign matter debris from entering the air inlet (34) of the engine (12).

Solution 23. apparatus (50) according to solution 22, characterized in that the tubular cross-members (74, 84, 74, 174, 184, 274, 284, 374, 384) are in a first layer (73) and solid wire links are positioned in a second layer (83) such that the first layer (73) and the second layer (83) together define a mesh (55).

The apparatus (50) of claim 16, wherein said aerodynamically efficient cross-section is tear-drop shaped.

Claim 25. the apparatus (50) of claim 24, wherein the tail of the cross-section is narrow.

Claim 26. the apparatus (50) of claim 24, wherein the tail of the cross-section is pointed.

Claim 27. the apparatus (50) of claim 24, wherein the tail of the cross-section is circular.

The apparatus (50) of claim 16, wherein the aerodynamically efficient cross-section is substantially diamond-shaped.

Claim 29. the apparatus (50) of claim 28, wherein one end of the cross-section is substantially circular.

Solution 30. the apparatus (50) according to solution 29, wherein both ends of the cross-section are rounded.

Drawings

The invention may best be understood by reference to the following description taken in conjunction with the accompanying drawings, in which:

FIG. 1 shows a perspective view of an aircraft engine including a plurality of FOD mesh screens according to the present invention;

fig. 2 shows a plan view of a mesh screen according to the present invention;

fig. 3 shows a side cross-sectional view of the mesh screen taken along line 3-3 shown in fig. 2;

FIG. 4 shows a radial expanded view of a set of screens with associated sections of the engine;

fig. 5 shows a section of a mesh screen;

fig. 6 shows a section of the intersection of two tubes in a mesh screen; and

fig. 7-10 show cross-sections of various wires according to alternative embodiments of the present invention.

Parts list

12 engine

14 propeller assembly

16 engine shell

22 exhaust pipe

32 air inlet duct

34 air inlet

38 mesh screen assembly

50 mesh screen

53 frame

55 unheated web

70 heated screen assembly

73 first layer

74 first layer pipe

83 second layer

84 second layer pipe

92 intersection

94 mesh screen openings

174 tube/cross member

274 tube/cross member

374 tube/cross member

474 tubes/cross members.

Detailed Description

Referring to the drawings, wherein like reference numbers refer to like elements throughout the various views, fig. 1 shows an engine 12 that includes a plurality of mesh screens 50 arranged in a mesh screen assembly 38 such that each of the mesh screens 50 covers an air inlet 34. The engine 12 also includes a propeller assembly 14, a housing 16, a pair of exhaust pipes 22, and a mounting block 28. In the illustrated embodiment, the engine 12 is a turboprop aircraft engine. In other embodiments, the engine 12 may be configured for use in marine and industrial applications.

Referring now to fig. 2, a section of the mesh assembly 38 is shown such that an example mesh 50 is presented in plan view. The mesh screen 50 includes a frame 53 configured to support a mesh assembly 70. In the illustrated embodiment, the frame 53 is a tubular structure and is configured to support a mesh 55. The mesh 55 is configured to allow air from outside the engine 12 to pass through the air inlet 34 and into the air inlet duct 32 while preventing Foreign Object Debris (FOD) from entering the air inlet duct 32 (see fig. 3).

The netting assembly 70 also includes a first layer 73 of first layer tubes 74 positioned offset from and in contact with a second layer 83 of second layer tubes 84. The first and

second layers

73, 83 are positioned relative to each other such that the first and second layers of

tubes

74, 84 intersect to define a plurality of intersections 92.

Tubes

74 and 84 are cross-members configured to block FOD. With continued reference to fig. 2 and 5, a plurality of mesh screen openings 94 are defined by portions of the first layer of tubes 74 and the second layer of tubes 84 and the intersections 92. The openings 94 are sized such that FODs exceeding a predetermined size and shape cannot pass through.

The relative positions of the first layer 73 and the second layer 83 may vary from embodiment to embodiment. In some embodiments, first layer 73 and second layer 83 are not offset and are on the same plane. In other embodiments, the first layer 73 and the second layer 83 are spaced apart from each other. In yet other embodiments, there may be more than two layers, and some layers may be in contact with each other and some layers may be spaced apart from each other.

In addition, the number of openings 94 in each mesh screen 50 is also selected to allow a predetermined air flow through the mesh screen 50. It is believed that the aerodynamically efficient tubular structure of a portion of the mesh screen 50 may provide additional strength at a lighter weight than provided by a similarly sized solid member.

Referring now to fig. 4, there is shown in radially expanded view a mesh screen assembly 38 comprising a partial section of a plurality of struts 31. The mesh screens 50 are radially distributed around the engine 12, and each of the mesh screens 50 is positioned over an associated air inlet 34 and air inlet duct 32. The air inlet duct 32 is defined by the struts 31.

The

tubes

74 and 84 are configured such that their respective cross-sections are not circular, but are aerodynamically shaped, and therefore, aerodynamically efficient. As used herein, the term "aerodynamic shape" refers to the shape of an object: it is configured to pass through air such that not as much turbulence and/or air resistance is generated around the object as is the case when the object is generally circular (such as a circular wire). As used herein, the term "aerodynamically efficient" refers to the characteristic that the ratio of air resistance to thickness or diameter is less than that of a structure having a generally circular cross-section of an object, such as a circular wire. Generally, the

tubes

74 and 84 in a single embodiment have the same external shape as shown in fig. 3, but it should be understood that the shapes of the

tubes

74 and 84 may be mixed within a given mesh screen 50. As can be seen in fig. 3 and 6-10, aerodynamically efficient shapes may vary from embodiment to embodiment, and may be shapes other than those described herein.

One aerodynamically efficient shape for subsonic speeds is a tear drop shape, as illustrated by the cross-section of tube 174 shown in fig. 7. The tear drop shape is symmetric about an axis extending from the circular front to the tapered tip. Another aerodynamically efficient shape is the symmetrical anterior and posterior diamond shape of tube 274 shown in fig. 8 with narrow noses and tails. A third aerodynamically efficient shape is the airfoil illustrated by tube 374 and shown in fig. 9. The tube 374 has a convex side that curves away from an opposite concave side as shown. Another variation of the airfoil shape is shown in fig. 10, where tube 474 is a truncated airfoil with a smaller curvature on the concave side and a rounded tail as compared to tube 374. For sub-sonic velocities, the most aerodynamically efficient shape is the teardrop shape.

The foregoing has described an apparatus for providing an aerodynamically efficient FOD mesh screen. Due to the aerodynamic efficiency of the FOD screens described above, they provide protection with less energy waste. Such mesh screens may be used in any machine or application that requires a FOD-free fluid, such as air and other gases or liquids. Such other applications include IC engines, fans, cooling water, oils, and the like. All of the features disclosed in this specification (including any accompanying claims, abstract and drawings), and/or all of the steps of any method or process so disclosed, may be combined in any combination, except combinations where at least some of such features and/or steps are mutually exclusive.

Each feature disclosed in this specification (including any accompanying claims, abstract and drawings) may be replaced by alternative features serving the same, equivalent or similar purpose, unless expressly stated otherwise. Thus, unless expressly stated otherwise, each feature disclosed is one example only of a generic series of equivalent or similar features.

The invention is not limited to the details of the foregoing embodiment(s). The invention extends to any novel one, or any novel combination, of the features disclosed in this specification (including any accompanying novel points, abstract and drawings), or to any novel one, or any novel combination, of the steps of any method or process so disclosed.

Claims

1. An apparatus for providing foreign object debris protection to an air inlet of an aircraft engine, the apparatus comprising;

a frame;

a plurality of cross members positioned in the frame to define a plurality of mesh screen openings;

wherein the plurality of cross members comprise a first layer of first layer tubes positioned offset from and in contact with a second layer of second layer tubes such that the first layer and the second layer are in different planes offset from each other, an upper side of the first layer is in contact with an underside of the second layer in the direction of offset, and the first layer tubes and the second layer tubes cross to define a plurality of intersections defining the plurality of mesh screen openings, and

wherein the first and second layer of tubes each have a tear drop shaped cross section or the first and second layer of tubes each have a diamond shaped cross section.

2. The apparatus of claim 1, wherein the plurality of cross members are tubular cross members.

3. The apparatus of claim 2, wherein the frame is configured to support a mesh assembly formed by the tubular cross-members.

4. The apparatus of claim 3, wherein the frame is further configured to support a web that is not configured to be heated.

5. The apparatus of claim 4, wherein the tubular cross members are arranged in layers and positioned parallel to each other.

6. The apparatus of claim 5, wherein the tubular cross members are arranged in two layers such that the tubular cross members in each layer are parallel to the tubular cross members in that layer as well, and the tubular cross members in each layer cross the tubular cross members of the other layer to form a mesh.

7. The apparatus of claim 6, wherein the mesh is configured to prevent foreign matter debris from entering the air inlet of the engine.

8. The apparatus of claim 7, wherein the tubular cross-members are in a first tier and solid wire links are positioned in a second tier such that the first tier and the second tier collectively define a mesh.

9. The apparatus of claim 1, wherein the first and second layers of tubes each have a tear drop shaped cross section with a tail of the cross section being narrow.

10. The apparatus of claim 1, wherein the first and second layer of tubes each have a tear drop shaped cross section with a tail of the cross section being pointed.

11. The apparatus of claim 1, wherein the first and second layer of tubes each have a tear drop shaped cross section with a tail of the cross section being circular.

12. The apparatus of claim 1, wherein the first and second layers of pipe each have a diamond shaped cross section with one end of the cross section being circular.

13. The apparatus of claim 1, wherein the first and second layers of pipe each have a diamond shaped cross section with both ends of the cross section being rounded.